Airworthiness Directives; Bell Helicopter Textron Canada Model 222, 222B, 222U, 230 and 430 Helicopters, 3889-3891 [E8-1026]
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Federal Register / Vol. 73, No. 15 / Wednesday, January 23, 2008 / Proposed Rules
(A) If the torque is below the minimum
required amount, replace the tailboom
attachment bolt in accordance with the
Accomplishment Instructions, Part II, step 1
of the applicable ASB listed in Table I of this
AD.
(B) If the torque is above the maximum
amount, adjust the torque to within the
allowable range.
(ii) If an incorrect number or type of
washer is installed or the tailboom
attachment bolt is oriented in the wrong
direction, reconfigure as necessary to meet
the requirements of the Notes on Figure 1 of
the applicable ASB listed in Table I of this
AD.
(iii) If there is less than 1 tailboom
attachment bolt thread exposed, adjust the
number of washers and retorque the nut so
that between 1 and 3 tailboom attachment
bolt threads are exposed at the proper nut
torque.
(iv) If more than 3 tailboom attachment
bolt threads are exposed, replace the
attachment bolt in accordance with the
Accomplishment Instructions, Part II, step 1
of the applicable ASB listed in Table 1 of this
AD.
(2) If a tailboom attachment bolt must be
replaced based on a requirement of this AD,
at 100 hours TIS after the tailboom
attachment bolt is replaced, do a torque
check of the nut.
Differences Between the FAA AD and the
MCAI
(f) None.
ebenthall on PROD1PC69 with PROPOSALS
Subject
(g) Air Transport Association of America
(ATA) Code 5340, Fuselage Main, Attach
Fittings.
Other Information
(h) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Safety Management
Group, Rotorcraft Directorate, FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN:
Sharon Miles, Aerospace Engineer; Fort
Worth, Texas 76193–0111, telephone (817)
222–5122, fax (817) 222–5961.
(2) Airworthy Product: Use only FAAapproved corrective actions. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent) if the State of
Design has an appropriate bilateral agreement
with the United States. You are required to
assure the product is airworthy before it is
returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(i) MCAI Transport Canada Airworthiness
Directive CF–2007–01, dated January 19,
2007, contains related information.
VerDate Aug<31>2005
15:07 Jan 22, 2008
Jkt 214001
Issued in Fort Worth, Texas, on January 9,
2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–1025 Filed 1–22–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0039; Directorate
Identifier 2006–SW–13–AD]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada Model 222,
222B, 222U, 230 and 430 Helicopters
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This document proposes
adopting a new airworthiness directive
(AD) for Bell Helicopter Textron Canada
(BHTC) Model 222, 222B, 222U, 230
and 430 helicopters. This proposal
would require rewiring and testing the
fuel valve switch on each engine and
testing the ignitor system. This proposal
is prompted by an in-flight incident in
which a fuel valve switch failed,
causing the fuel valve to inadvertently
close. The actions specified by this
proposed AD are intended to prevent
interruption of the fuel supply caused
by failure of the fuel switch, which
could result in loss of engine power and
subsequent loss of control of the
helicopter.
Comments must be received on
or before March 24, 2008.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
You may get the service information
identified in this proposed AD from Bell
DATES:
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
3889
Helicopter Textron Canada, 12,800 Rue
de l’Avenir, Mirabel, Quebec J7J1R4,
telephone (450) 437–2862 or (800) 363–
8023, fax (450) 433–0272.
You may examine the comments to
this proposed AD in the AD docket on
the Internet at https://
www.regulations.gov.
FOR FURTHER INFORMATION CONTACT:
Carroll Wright, Aviation Safety
Engineer, FAA, Rotorcraft Directorate,
Regulations and Policy Group, Fort
Worth, Texas 76193–0110, telephone
(817) 222–5120, fax (817) 222–5961.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written
data, views, or arguments regarding this
proposed AD. Send your comments to
the address listed under the caption
ADDRESSES. Include the docket number
‘‘FAA–2008–0039, Directorate Identifier
2006–SW–13–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed
rulemaking. Using the search function
of our docket web site, you can find and
read the comments to any of our
dockets, including the name of the
individual who sent or signed the
comment. You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
2000 (65 FR 19477–78), or you may visit
https://www.regulations.gov.
Examining the Docket
You may examine the docket that
contains the proposed AD, any
comments, and other information in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Operations office (telephone
(800) 647–5527) is located in Room
W12–140 on the ground floor of the
West Building at the street address
stated in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
Discussion
This document proposes adopting a
new AD for the following BHTC
helicopters:
E:\FR\FM\23JAP1.SGM
23JAP1
3890
Federal Register / Vol. 73, No. 15 / Wednesday, January 23, 2008 / Proposed Rules
Model No.
Serial Nos.
222 ..........................
222B ........................
222U .......................
230 ..........................
430 ..........................
47006
47131
47501
23001
49001
through
through
through
through
through
47089.
47156.
47574.
23038.
49101.
This proposal would require, within 50
hours time-in-service (TIS), rewiring the
switches that control the operation of
the No. 1 and No. 2 engines’ fuel valves,
and testing the switches and the ignitor
system. This proposal is prompted by an
in-flight incident in which a fuel valve
switch failed. The manufacturer reports
that there is a possibility that a switch
may fail during flight due to vibration,
causing the switch to open and then
causing the fuel valve to close, resulting
in inadvertent shut down of an engine.
The actions specified by this proposed
AD are intended to prevent interruption
of the fuel supply caused by failure of
the fuel switch, which could result in
loss of engine power and subsequent
loss of control of the helicopter.
Transport Canada, the airworthiness
authority for Canada, notified the FAA
that an unsafe condition may exist on
BHTC Model 222, 222B, 222U, 230 and
430 helicopters. Transport Canada
advises of an investigation into an
incident involving a BHTC Model 222
helicopter, in which the fuel shut-off
switch, part number (P/N) 10648BH1–1,
failed during flight causing the fuel
valve to close and the engine to shut
down. Review of the Service Difficulty
Report database identified two other
incidents of switch failure.
Bell Helicopter Textron has issued the
following technical bulletins, all dated
June 11, 2003, which specify rewiring
the fuel valve switch:
Technical
bulletin
Helicopter models affected
No. 222–03–171
Model 222 and 222B helicopters.
Model 222U helicopters.
ebenthall on PROD1PC69 with PROPOSALS
No. 222U–03–
96.
No. 230–03–35
No. 430–03–33
Model 230 helicopters.
Model 430 helicopters.
Transport Canada classified these
technical bulletins as mandatory and
issued AD No. CF–2006–03, dated
February 28, 2006, to ensure the
continued airworthiness of these
helicopters in Canada. That AD requires
compliance no later than May 3, 2006.
This proposal would require
compliance within 50 hours TIS.
This helicopter model is
manufactured in Canada and is type
certificated for operation in the United
States under the provisions of 14 CFR
21.29 and the applicable bilateral
VerDate Aug<31>2005
15:07 Jan 22, 2008
Jkt 214001
agreement. Pursuant to the applicable
bilateral agreement, Transport Canada
has kept us informed of the situation
described above. We have examined the
findings of Transport Canada, reviewed
all available information, and
determined that AD action is necessary
for products of these type designs that
are certificated for operation in the
United States.
This previously described unsafe
condition is likely to exist or develop on
other helicopters of these same type
designs registered in the United States.
Therefore, the proposed AD would
require, within 50 hours TIS, rewiring
the switches, P/N 10648BH1–1, located
in the cockpit overhead console, that
control the operation of the No. 1 and
No. 2 engines’ fuel valves. The actions
would be required to be accomplished
by following the specified portions of
the technical bulletins described
previously.
We estimate that this proposed AD
would affect 165 helicopters of U.S.
registry and the proposed actions would
take approximately four work hours per
helicopter to rewire the 2 fuel valve
switches, and test those switches and
the ignitor system at an average labor
rate of $80 per work hour. Based on
these figures, we estimate the total cost
impact of the proposed AD on U.S.
operators to be $52,800 ($320 per
helicopter).
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. Additionally, this proposed AD
would not have a substantial direct
effect on the States, on the relationship
between the national Government and
the States, or on the distribution of
power and responsibilities among the
various levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a draft economic
evaluation of the estimated costs to
comply with this proposed AD. See the
AD docket to examine the draft
economic evaluation.
1. The authority citation for part 39
continues to read as follows:
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration proposes to amend part
39 of the Federal Aviation Regulations
(14 CFR part 39) as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Section 39.13 is amended by
adding a new airworthiness directive to
read as follows:
Bell Helicopter Textron Canada: Docket No.
FAA–2008–0039; Directorate Identifier
2006–SW–13–AD.
Applicability: The following model
helicopters, certificated in any category:
Model No.
222 ..........................
222B ........................
222U .......................
230 ..........................
430 ..........................
Serial Nos.
47006
47131
47501
23001
49001
through
through
through
through
through
47089.
47156.
47574.
23038.
49101.
Compliance: Required within 50 hours
time-in-service, unless accomplished
previously.
To prevent interruption of the fuel supply
caused by failure of the fuel switch, which
could result in loss of engine power and
subsequent loss of control of the helicopter,
accomplish the following:
(a) Rewire the No. 1 and No. 2 engines’ fuel
valve switch, part number 10648BH1–1, and
test the fuel valve switches and the ignitor
system, in accordance with the
E:\FR\FM\23JAP1.SGM
23JAP1
Federal Register / Vol. 73, No. 15 / Wednesday, January 23, 2008 / Proposed Rules
Accomplishment Instructions in Bell
Helicopter Textron Technical Bulletin (TB)
No. 222–03–171, Part 1, applicable to Model
222 helicopters, serial number (S/N) 47006–
47038, and Part 2, applicable to Model 222
helicopters, S/N 47039–47089, and Model
222B helicopters, S/N 47131–47156; TB No.
222U–03–96, applicable to Model 222U
helicopters; TB No. 230–03–35, applicable to
Model 230 helicopters; and TB No. 430–03–
33, applicable to Model 430 helicopters. All
of the technical bulletins are dated June 11,
2003.
(b) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Regulations and
Policy Group, FAA, ATTN: Carroll Wright,
2601 Meacham Blvd., Fort Worth, Texas
76193–0110, telephone (817) 222–5120, fax
(817) 222–5961, for information about
previously approved alternative methods of
compliance.
Note: The subject of this AD is addressed
in Transport Canada (Canada) AD CF–2006–
03, dated February 28, 2006.
Issued in Fort Worth, Texas, on January 8,
2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–1026 Filed 1–22–08; 8:45 am]
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0041; Directorate
Identifier 2007–SW–16–AD]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Model AS 355 N Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
ebenthall on PROD1PC69 with PROPOSALS
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
Eurocopter France (Eurocopter) Model
AS 355 N helicopters. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The European Aviation Safety
Agency (EASA), the technical Agent for
France, with which we have a bilateral
agreement states in the MCAI:
This Airworthiness Directive (AD) is
issued because it was found that the power
drawn by the starter generators from the
engines is above the consumption capacity at
altitudes above 3,000 meters, declared for the
engines of AS 355 N helicopters.
15:07 Jan 22, 2008
After engine start, the starter generator
functions as the normal operational
electrical generator.
The proposed AD would require
actions that are intended to address this
unsafe condition.
DATES: We must receive comments on
this proposed AD by February 22, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building, Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building, Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590 between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
Examining the AD Docket
DEPARTMENT OF TRANSPORTATION
VerDate Aug<31>2005
Excessive power consumption of the starter
generators reduces the engine surge margin,
which can result in engine failure.
Jkt 214001
You may examine the AD docket on
the Internet at https://
www.regulations.gov, or in person at the
Docket Operations Office Facility
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this proposed
AD, the economic evaluation, any
comments received, and other
information. The street address for the
Docket Operations Office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Ed
Cuevas, Aviation Safety Engineer, FAA,
Rotorcraft Directorate, Safety
Management Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5355,
fax (817) 222–5961.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
3891
unsafe conditions on U.S.-certificated
products.
This proposed AD references the
MCAI and related service information
that we considered in forming the
engineering basis to correct the unsafe
condition. The proposed AD contains
text copied from the MCAI and for this
reason might not follow our plain
language principles.
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0041; Directorate Identifier
2007–SW–16–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued an MCAI in the
form of EASA Airworthiness Directive
2006–0338, dated November 7, 2006
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for these
French-certificated products. The MCAI
states:
This Airworthiness Directive (AD) is
issued because it was found that the power
drawn by the starter generators from the
engines is above the consumption capacity at
altitudes above 3,000 meters, declared for the
engines of AS 355 N helicopters.
Excessive power consumption of the starter
generators reduces the engine surge margin,
which can result in engine failure.
The starter-generator is a single unit
that operates as both an engine starter
generator and after starting, as an
operational generator. The EASA AD
and the Eurocopter service bulletin refer
to this unit as a starter generator when
used as a generator. The starter
generator requires energy from the
engine to generate electricity. When the
electrical current exceeds 100 amps, the
load on the engine reduces the engine
surge margin and may cause the engine
to surge and flame out.
Therefore, at altitudes above 10,000
feet, the maximum continuous current
E:\FR\FM\23JAP1.SGM
23JAP1
]]>Agencies
[Federal Register Volume 73, Number 15 (Wednesday, January 23, 2008)]
[Proposed Rules]
[Pages 3889-3891]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-1026]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0039; Directorate Identifier 2006-SW-13-AD]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada Model
222, 222B, 222U, 230 and 430 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes adopting a new airworthiness directive
(AD) for Bell Helicopter Textron Canada (BHTC) Model 222, 222B, 222U,
230 and 430 helicopters. This proposal would require rewiring and
testing the fuel valve switch on each engine and testing the ignitor
system. This proposal is prompted by an in-flight incident in which a
fuel valve switch failed, causing the fuel valve to inadvertently
close. The actions specified by this proposed AD are intended to
prevent interruption of the fuel supply caused by failure of the fuel
switch, which could result in loss of engine power and subsequent loss
of control of the helicopter.
DATES: Comments must be received on or before March 24, 2008.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
You may get the service information identified in this proposed AD
from Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel,
Quebec J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450)
433-0272.
You may examine the comments to this proposed AD in the AD docket
on the Internet at https://www.regulations.gov.
FOR FURTHER INFORMATION CONTACT: Carroll Wright, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group,
Fort Worth, Texas 76193-0110, telephone (817) 222-5120, fax (817) 222-
5961.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written data, views, or arguments
regarding this proposed AD. Send your comments to the address listed
under the caption ADDRESSES. Include the docket number ``FAA-2008-0039,
Directorate Identifier 2006-SW-13-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this proposed rulemaking. Using the
search function of our docket web site, you can find and read the
comments to any of our dockets, including the name of the individual
who sent or signed the comment. You may review the DOT's complete
Privacy Act Statement in the Federal Register published on April 11,
2000 (65 FR 19477-78), or you may visit https://www.regulations.gov.
Examining the Docket
You may examine the docket that contains the proposed AD, any
comments, and other information in person at the Docket Operations
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Operations office (telephone (800) 647-5527) is
located in Room W12-140 on the ground floor of the West Building at the
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
Discussion
This document proposes adopting a new AD for the following BHTC
helicopters:
[[Page 3890]]
------------------------------------------------------------------------
Model No. Serial Nos.
------------------------------------------------------------------------
222................................ 47006 through 47089.
222B............................... 47131 through 47156.
222U............................... 47501 through 47574.
230................................ 23001 through 23038.
430................................ 49001 through 49101.
------------------------------------------------------------------------
This proposal would require, within 50 hours time-in-service (TIS),
rewiring the switches that control the operation of the No. 1 and No. 2
engines' fuel valves, and testing the switches and the ignitor system.
This proposal is prompted by an in-flight incident in which a fuel
valve switch failed. The manufacturer reports that there is a
possibility that a switch may fail during flight due to vibration,
causing the switch to open and then causing the fuel valve to close,
resulting in inadvertent shut down of an engine. The actions specified
by this proposed AD are intended to prevent interruption of the fuel
supply caused by failure of the fuel switch, which could result in loss
of engine power and subsequent loss of control of the helicopter.
Transport Canada, the airworthiness authority for Canada, notified
the FAA that an unsafe condition may exist on BHTC Model 222, 222B,
222U, 230 and 430 helicopters. Transport Canada advises of an
investigation into an incident involving a BHTC Model 222 helicopter,
in which the fuel shut-off switch, part number (P/N) 10648BH1-1, failed
during flight causing the fuel valve to close and the engine to shut
down. Review of the Service Difficulty Report database identified two
other incidents of switch failure.
Bell Helicopter Textron has issued the following technical
bulletins, all dated June 11, 2003, which specify rewiring the fuel
valve switch:
------------------------------------------------------------------------
Technical bulletin Helicopter models affected
------------------------------------------------------------------------
No. 222-03-171........................ Model 222 and 222B helicopters.
No. 222U-03-96........................ Model 222U helicopters.
No. 230-03-35......................... Model 230 helicopters.
No. 430-03-33......................... Model 430 helicopters.
------------------------------------------------------------------------
Transport Canada classified these technical bulletins as mandatory and
issued AD No. CF-2006-03, dated February 28, 2006, to ensure the
continued airworthiness of these helicopters in Canada. That AD
requires compliance no later than May 3, 2006. This proposal would
require compliance within 50 hours TIS.
This helicopter model is manufactured in Canada and is type
certificated for operation in the United States under the provisions of
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the
applicable bilateral agreement, Transport Canada has kept us informed
of the situation described above. We have examined the findings of
Transport Canada, reviewed all available information, and determined
that AD action is necessary for products of these type designs that are
certificated for operation in the United States.
This previously described unsafe condition is likely to exist or
develop on other helicopters of these same type designs registered in
the United States. Therefore, the proposed AD would require, within 50
hours TIS, rewiring the switches, P/N 10648BH1-1, located in the
cockpit overhead console, that control the operation of the No. 1 and
No. 2 engines' fuel valves. The actions would be required to be
accomplished by following the specified portions of the technical
bulletins described previously.
We estimate that this proposed AD would affect 165 helicopters of
U.S. registry and the proposed actions would take approximately four
work hours per helicopter to rewire the 2 fuel valve switches, and test
those switches and the ignitor system at an average labor rate of $80
per work hour. Based on these figures, we estimate the total cost
impact of the proposed AD on U.S. operators to be $52,800 ($320 per
helicopter).
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. Additionally, this proposed
AD would not have a substantial direct effect on the States, on the
relationship between the national Government and the States, or on the
distribution of power and responsibilities among the various levels of
government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a draft economic evaluation of the estimated costs to
comply with this proposed AD. See the AD docket to examine the draft
economic evaluation.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (14 CFR part 39) as
follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
Bell Helicopter Textron Canada: Docket No. FAA-2008-0039;
Directorate Identifier 2006-SW-13-AD.
Applicability: The following model helicopters, certificated in
any category:
------------------------------------------------------------------------
Model No. Serial Nos.
------------------------------------------------------------------------
222................................ 47006 through 47089.
222B............................... 47131 through 47156.
222U............................... 47501 through 47574.
230................................ 23001 through 23038.
430................................ 49001 through 49101.
------------------------------------------------------------------------
Compliance: Required within 50 hours time-in-service, unless
accomplished previously.
To prevent interruption of the fuel supply caused by failure of
the fuel switch, which could result in loss of engine power and
subsequent loss of control of the helicopter, accomplish the
following:
(a) Rewire the No. 1 and No. 2 engines' fuel valve switch, part
number 10648BH1-1, and test the fuel valve switches and the ignitor
system, in accordance with the
[[Page 3891]]
Accomplishment Instructions in Bell Helicopter Textron Technical
Bulletin (TB) No. 222-03-171, Part 1, applicable to Model 222
helicopters, serial number (S/N) 47006-47038, and Part 2, applicable
to Model 222 helicopters, S/N 47039-47089, and Model 222B
helicopters, S/N 47131-47156; TB No. 222U-03-96, applicable to Model
222U helicopters; TB No. 230-03-35, applicable to Model 230
helicopters; and TB No. 430-03-33, applicable to Model 430
helicopters. All of the technical bulletins are dated June 11, 2003.
(b) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Manager, Regulations and Policy Group, FAA, ATTN:
Carroll Wright, 2601 Meacham Blvd., Fort Worth, Texas 76193-0110,
telephone (817) 222-5120, fax (817) 222-5961, for information about
previously approved alternative methods of compliance.
Note: The subject of this AD is addressed in Transport Canada
(Canada) AD CF-2006-03, dated February 28, 2006.
Issued in Fort Worth, Texas, on January 8, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-1026 Filed 1-22-08; 8:45 am]
BILLING CODE 4910-13-P
